Aerospace Science and Technology最新文献_第8页

Fast trajectory optimization with time-varying chance-constrained model predictive control of quadcopters for dynamic collision avoidance 基于时变机会约束模型的四轴飞行器动态避碰快速轨迹优化预测控制

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111815

D.M.K.K. Venkateswara Rao , Hamed Habibi , Holger Voos

In this paper, we propose a parallelized optimization-based framework for autonomous and safe control of quadrotor Unmanned Aerial Vehicles (UAVs). We achieve this by designing a real-time optimal trajectory planner and a time-varying collision chance-constrained model predictive controller. We consider an obstacle with unknown dynamics in the operational space of the UAV and plan time-optimal transfer maneuvers using the shifted Chebyshev pseudospectral method. We propose a novel sigmoid function-based approximation to the conditional collision avoidance constraint of UAV trajectory segments and enable automatic differentiation for achieving real-time implementation. Given the uncertain positions of the UAV and the obstacle, we propose a time-varying probability margin for the collision avoidance constraint and design a chance-constrained model predictive controller to track the reference optimal trajectory with minimum tracking error and avoid collisions in real-time. Moreover, we parallelize the trajectory planner and the controller to address their asynchronous computational execution. The scalability and effectiveness of the proposed architecture are evaluated by performance analysis through Monte Carlo and numerical simulations. Finally, the real-time feasibility of the integrated approach is validated by indoor high-speed maneuvers and dynamic collision avoidance experiments.

本文提出了一种基于并行优化的四旋翼无人机自主安全控制框架。我们通过设计实时最优轨迹规划器和时变碰撞机会约束模型预测控制器来实现这一目标。考虑无人机作战空间中存在未知动力学障碍，利用移位切比雪夫伪谱法规划时间最优转移机动。我们提出了一种新的基于s型函数的无人机轨迹段条件避碰约束近似方法，并实现了自动微分，实现了实时实现。针对无人机和障碍物位置的不确定性，提出了时变概率裕度的避碰约束，设计了机会约束模型预测控制器，以最小的跟踪误差跟踪参考最优轨迹，实现了实时避碰。此外，我们将轨迹规划器和控制器并行化，以解决它们的异步计算执行问题。通过蒙特卡罗性能分析和数值模拟，对该体系结构的可扩展性和有效性进行了评价。最后，通过室内高速机动和动态避碰实验验证了该综合方法的实时性可行性。

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引用次数: 0

Task allocation with communication coordination in UAV swarms via asynchronous multi-Objective policy optimization 基于异步多目标策略优化的无人机群通信协调任务分配

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111760

Zehao Xiong, Yexun Xi, Yizhe Cao, Chuan Li, Rong Li, Jie Li

Task allocation in UAV swarms is becoming increasingly complex due to the complexity of tasks, communication limitations, and the robustness of the allocation algorithm. Combining reinforcement learning and task allocation demonstrates great potential in enhancing algorithm performance and optimizing communication. However, existing research has overlooked the structural conflict between task conflicts and communication overhead, which leads to significant challenges in exploration and training instability. To this end, this paper introduces the Task Allocation with Communication Coordination (TACC) method, which aims to train a gated mechanism strategy to coordinate communication timing while balancing transmission efficiency and allocation reliability. First, the TACC is formalized as a POMDP, for which the channel access and other features are designed to facilitate observations. Actions are inter-agent adaptive gating mechanisms, and the shared reward reflects global task conflicts. Second, to address the asynchronous learning under the CTDE, an asynchronous experience aggregation method is proposed to align trajectories from different agents. Then, the MOCPO is proposed, which applies constrained policy optimization directly to the policy gradient via a Lagrangian loss, thereby stabilizing gated communication early in training and enhancing sample efficiency and convergence. The computational complexity, boundary conditions, convergence, and communication complexity of the TACC are theoretically analyzed. Finally, sim-to-real experiments are conducted in the HIL environment, and the results demonstrate the optimal trade-off achieved by the proposed method and its overall state-of-the-art approaches. Ablation studies and hyperparameter experiments further validated the stability of MOCPO. Specifically, the communication strategy is effectively deployed in the RK3588 SOC, and the flight experiment demonstrates the superior scheduling outcomes of TACC within the ten-UAV swarm in the search and rescue scenario.

由于任务的复杂性、通信的局限性和分配算法的鲁棒性，无人机群中的任务分配变得越来越复杂。将强化学习与任务分配相结合，在提高算法性能和优化通信方面具有很大的潜力。然而，现有的研究忽略了任务冲突和通信开销之间的结构性冲突，这导致了探索和训练不稳定性方面的重大挑战。为此，本文引入了带有通信协调的任务分配（TACC）方法，该方法旨在训练一种门控机制策略来协调通信时序，同时平衡传输效率和分配可靠性。首先，将TACC形式化为POMDP，为POMDP设计通道访问和其他功能以方便观察。行为是agent间的自适应门控机制，共享奖励反映了全局任务冲突。其次，为了解决CTDE下的异步学习问题，提出了一种异步经验聚合方法来对齐来自不同智能体的轨迹。然后，提出了MOCPO算法，该算法通过拉格朗日损失直接对策略梯度进行约束策略优化，从而在训练早期稳定门控通信，提高样本效率和收敛性。从理论上分析了TACC的计算复杂度、边界条件、收敛性和通信复杂度。最后，在HIL环境中进行了模拟到真实的实验，结果证明了所提出的方法及其总体最新方法所实现的最佳权衡。烧蚀研究和超参数实验进一步验证了MOCPO的稳定性。具体而言，该通信策略在RK3588 SOC中得到了有效的部署，飞行实验验证了TACC在10架无人机群搜救场景下的优越调度效果。

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引用次数: 0

A General Analysis Framework for Multirotor Thrust-Vectoring Vehicles: From Configuration to Modeling to Data-Driven Approaches 多旋翼推力矢量飞行器的通用分析框架：从配置到建模再到数据驱动方法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111816

Yongjie Shu , Qingkai Meng , Shiyi Wei , Mingkai Ding , Yunyi Wang , Xixing Long , Zhifang Ke , Wei Wei

By actively modulating thrust directions, multi-rotor thrust-vector aerial vehicles (TVAVs) overcome the underactuation inherent in conventional coplanar multirotor systems, thereby enabling enhanced maneuverability, full-attitude control, and robust operation in confined or highly disturbed environments. With increasing structural complexity and actuation redundancy, research efforts have progressively evolved from configuration design and aerodynamic analysis toward system-level dynamic modeling and, more recently, data-driven methodologies. This paper presents a comprehensive review of the research evolution in multi-rotor TVAVs, beginning with a summary of configuration and structural analysis methods that explicitly consider thrust-vectoring layouts and aerodynamic effects, and their influence on attainable force spaces, aerodynamic force distribution, and control capabilities. Subsequently, dynamic modeling approaches and investigations into system dynamic properties are reviewed, together with model-based trajectory generation and full-attitude control methods that ensure dynamic feasibility. Furthermore, recent advances in data-driven and reinforcement learning–based methods are systematically discussed, highlighting their potential in addressing strong nonlinearities, model uncertainties, and aggressive maneuvering tasks. Finally, the advantages and limitations of different research paradigms are compared, and the central role of control allocation in thrust-vectoring control architectures is examined, with the aim of providing a structured perspective on the evolution from configuration analysis to dynamic modeling and data-driven methods, and of offering insights toward future unified frameworks that integrate structural constraints, aerodynamic characteristics, model-based design, and data-driven intelligence.

通过主动调节推力方向，多旋翼推力矢量飞行器（tvav）克服了传统共面多旋翼系统固有的欠驱动，从而增强了机动性、全姿态控制和在受限或高扰动环境下的鲁棒性。随着结构复杂性和驱动冗余的增加，研究工作逐渐从配置设计和空气动力学分析发展到系统级动态建模，以及最近的数据驱动方法。本文综述了多旋翼tvav的研究进展，首先总结了明确考虑推力矢量布局和气动效应的构型和结构分析方法，以及它们对可得力空间、气动力分布和控制能力的影响。随后，回顾了动态建模方法和对系统动态特性的研究，以及基于模型的轨迹生成和确保动态可行性的全姿态控制方法。此外，系统地讨论了数据驱动和基于强化学习的方法的最新进展，强调了它们在解决强非线性、模型不确定性和激进机动任务方面的潜力。最后，比较了不同研究范式的优势和局限性，并考察了控制分配在推力矢量控制体系结构中的核心作用，旨在为从配置分析到动态建模和数据驱动方法的演变提供结构化视角，并为整合结构约束、气动特性、基于模型的设计和数据驱动智能的未来统一框架提供见解。

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引用次数: 0

Static stability and control characteristics of the double-swept waveriders 双扫波器的静态稳定性及控制特性

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-03 DOI: 10.1016/j.ast.2026.111834

Shibin Luo, Shengxian Zheng, Jun Liu, Rui Liu, Daliang Yang

The double-swept waverider maintains excellent aerodynamic performance at high speeds while enhancing low-speed characteristics through vortex-lift effects, offering a promising approach for extending waverider applications across wide flight envelopes. However, existing research on this configuration has predominantly focused on basic aerodynamic features, with limited attention given to stability and controllability. To address this gap, a double-swept waverider with integrated control surfaces was designed using the projection method. And its lift-to-drag characteristics, static stability, and controllability across multiple speed regimes were systematically analyzed. Results indicate that the configuration consistently maintains static stability in both longitudinal and directional, whereas lateral static stability remains relatively weak. Longitudinal and directional control performance proves superior in subsonic conditions compared to supersonic and hypersonic regimes, while lateral controllability improves significantly under hypersonic conditions. Moreover, rudder deflection exerts minimal influence on pitch and roll channels, whereas differential elevon deflection induces significant pitch/yaw coupling effects.

双掠式乘波器在高速下保持了优异的空气动力学性能，同时通过涡流升力效应增强了低速特性，为跨宽飞行包线扩展乘波器的应用提供了一种有希望的方法。然而，现有的研究主要集中在基本的气动特性上，对稳定性和可控性的关注有限。为了解决这一问题，采用投影法设计了具有集成控制面的双扫描乘波器。系统分析了其升阻特性、静稳定性和多速度下的可控性。结果表明，该构型在纵向和方向上均保持稳定的静稳定性，而横向静稳定性相对较弱。与超音速和高超声速相比，纵向和方向控制性能在亚音速条件下被证明是优越的，而横向可控性在高超声速条件下显着提高。此外，方向舵偏转对俯仰和滚转通道的影响最小，而俯仰偏转对俯仰/偏航的耦合效应显著。

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引用次数: 0

Experimental optimization of novel B-shaped and C-shaped holes on flat plate and linear cascade models 平板上新型b形孔和c形孔的实验优化及线性级联模型

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 10.1016/j.ast.2026.111812

Haiwang Li , Yiming Luo , Zhiyu Zhou , Gang Xie , Long Meng , Yuzhu Lou

This study experimentally optimized B-shaped and C-shaped holes on the flat plate and linear cascade models to maximize cooling effectiveness. Adiabatic cooling effectiveness was measured via Pressure-Sensitive Paint experiments, and Response Surface Methodology was used for cooling effectiveness prediction. Additionally, Particle Image Velocimetry experiments were conducted to analyze the flow field. Film holes were arranged on the flat plate and at four streamwise positions of the vane, with a 45° injection angle and no compound angle. Blowing ratios ranged from 0.5 to 2.5 at a density ratio of 1.5. The mainstream Reynolds number based on hole diameter was 10⁴ for flat plate experiments, and 10⁶ based on chord length for cascade experiments. Optimization results further demonstrate the cooling potential of both curved expansion holes. B-shaped holes achieved a maximum effectiveness improvement of 29.6%, while C-shaped holes reached 46.7%. Optimized B-shaped and C-shaped holes suppressed coolant lift-off and achieved full film coverage. The enhanced performance is primarily attributed to the increased spanwise outlet width, which induces jet bifurcation and significantly strengthens lateral coolant spreading via intensified anti-counter-rotating vortex pairs. Optimization effectiveness was highest on the suction side, followed by the flat plate, and lowest on the pressure side. The influence of structural parameters on cooling effectiveness is independent of wall curvature, enabling the application of flat plate optimization results to the vane.

本研究对平板上的b形孔和c形孔以及线性叶栅模型进行了实验优化，以最大限度地提高冷却效果。通过压敏涂料实验测量绝热冷却效果，并采用响应面法进行冷却效果预测。此外，通过粒子图像测速实验对流场进行了分析。膜孔布置在平板上和叶片的四个流向位置，喷油角为45°，无复合角。吹风比为0.5至2.5，密度比为1.5。平板实验中基于孔径的主流雷诺数为10⁴，叶栅实验中基于弦长的主流雷诺数为10⁶。优化结果进一步证明了两种弯曲膨胀孔的冷却潜力。b型孔的效率提高幅度最大，为29.6%，c型孔的效率提高幅度最大，为46.7%。优化的b形孔和c形孔抑制了冷却剂的上升，实现了全膜覆盖。性能的提高主要是由于沿展向的出口宽度的增加，这引起了射流的分岔，并通过增强的反旋转涡对显著加强了冷却剂的横向扩散。吸力侧优化效果最高，平板次之，压力侧优化效果最低。结构参数对冷却效果的影响与壁面曲率无关，可以将平板优化结果应用于叶片。

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引用次数: 0

High-fidelity three-dimensional aerodynamic flow prediction on wings with physics-constrained dual-parallel attention UNet++ 基于物理约束的双平行注意unet++的高保真三维机翼气动流动预测

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 10.1016/j.ast.2026.111846

Rongfeng Cui (崔榕峰) , Qiao Zhang (张巧) , Weiwei Zhang (张伟伟) , Wenbo Lu (鲁文博) , Liangjie Gao (高亮杰)

Accurate flow field data provide a robust foundation for analyzing concentrated force distribution and implementing flow control strategies. Nevertheless, current deep neural network methods exhibit limitations in accuracy when applied to reconstruct three-dimensional wing flow fields. To address this challenge, we propose an intelligent flow field reconstruction technique termed physics-constrained Dual-Parallel Attention UNet++ (DPAtt-UNet++). This method utilizes the Unet++ neural network architecture as its backbone, integrating a dual-parallel attention mechanism and nested network structure. Furthermore, a physics-constrained hierarchical loss function is introduced, incorporating the residuals of the governing Navier-Stokes equations as soft constraints to enforce physical consistency during training. Comprehensive evaluations demonstrate that the proposed DPAtt-UNet++ outperforms not only the baseline U-Net by approximately 10% in reconstruction accuracy, but also shows clear improvements over both standard UNet++ and a non-physics-constrained DPAtt-UNet++, validating the effectiveness of the integrated attention mechanism and physical constraints. Tests on wings constructed from different airfoil profiles confirm robust generalization capability across varying flow conditions and geometric shapes. Moreover, the method achieves approximately 2–3 orders of magnitude faster reconstruction speed compared to the Computational Fluid Dynamics (CFD) method in the online prediction phase. These results demonstrate the method can accurately and efficiently reconstruct flow fields for different geometries under various flow conditions.

准确的流场数据为分析集中力分布和实施流动控制策略提供了坚实的基础。然而，目前的深度神经网络方法在重建三维机翼流场时存在精度上的局限性。为了解决这一挑战，我们提出了一种智能流场重建技术，称为物理约束双并行注意力UNet++ (DPAtt-UNet++)。该方法以unet++神经网络架构为骨干，集成了双并行注意力机制和嵌套网络结构。此外，引入了物理约束的分层损失函数，将控制Navier-Stokes方程的残差作为软约束，以加强训练期间的物理一致性。综合评估表明，所提出的DPAtt-UNet++不仅在重建精度上优于基线U-Net约10%，而且在标准UNet++和非物理约束DPAtt-UNet++的基础上都有明显改进，验证了综合注意力机制和物理约束的有效性。对不同翼型结构的机翼进行了测试，证实了在不同流动条件和几何形状下的强大泛化能力。在在线预测阶段，该方法的重建速度比计算流体力学（CFD）方法快约2-3个数量级。结果表明，该方法可以准确、有效地重建不同几何形状、不同流动条件下的流场。

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引用次数: 0

Investigation on the cooling characteristics of turbine blades with bionic fractal channels under typical gas-thermal parameters 典型气热参数下仿生分形通道涡轮叶片冷却特性研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 10.1016/j.ast.2026.111842

Xinzi Liu , Longfei Wang , Wang Lei , Junkui Mao , Chengliang Lv , Dewei Zhang , Yiming Liu , Zhongran Chi

Fractal channels, characterized by high surface-to-volume ratio and geometric flexibility, demonstrate significant potential in turbine blade cooling design. This study experimentally and numerically investigates a turbine blade equipped with a tree-like bionic fractal channel under multi-parameter coupling working conditions, focusing on the effects of blowing ratio, temperature ratio, and mainstream Reynolds number. The results indicate that the three parameters independently influence blade cooling effectiveness with minimal coupling interaction. As temperature ratio increases, the sensitivity of cooling effectiveness to blowing ratio amplifies significantly. Cooling effectiveness improves with higher blowing ratio and lower reynolds number, showing the greatest responsiveness to blowing ratio variations. Consequently, optimal design of bionic fractal cooling architectures must account for operational parameters. The spatial distribution density of tree-like bionic fractal channels at the mid-chord position notably affects localized cooling characteristics, with a 6.5 % enhancement observed in the test region upon increasing channel number. A systematic reduction in fractal channel inlet diameter along the chordwise direction regulates cooling air mass flow rate to match spatially varying heat loads, resulting in a 150 % disparity in internal wall heat transfer coefficients between the blade leading and trailing edges. These findings confirm that fractal channel configuration and geometric parameters are primary factors influencing cooling effectiveness distribution through localised flow modulation, establishing them as critical optimisation targets.

分形通道具有高表面体积比和几何灵活性的特点，在涡轮叶片冷却设计中显示出巨大的潜力。实验和数值研究了多参数耦合工况下具有树状仿生分形通道的涡轮叶片，重点研究了吹风比、温度比和主流雷诺数对叶片的影响。结果表明，三个参数对叶片冷却效果的影响是独立的，且耦合作用最小。随着温度比的增大，冷却效果对吹气比的敏感性显著增强。吹气比越高、雷诺数越低，冷却效果越好，对吹气比变化的响应性越强。因此，仿生分形冷却结构的优化设计必须考虑运行参数。中弦位置树形仿生分形通道的空间分布密度显著影响局部冷却特性，随着通道数量的增加，测试区域的局部冷却特性增强了6.5%。分形通道入口直径沿弦向的系统性减小调节了冷却空气质量流量，以匹配空间变化的热负荷，导致叶片前后缘的内壁传热系数相差150%。这些发现证实了分形通道结构和几何参数是影响局部流动调制冷却效率分布的主要因素，并将其作为关键优化目标。

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引用次数: 0

Design and simulation research on local acceleration/deceleration profiles in supersonic flow 超声速流动中局部加减速剖面的设计与仿真研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-02 DOI: 10.1016/j.ast.2026.111825

Saiqiang Zhang , Gang Li , Wanwu Xu , Jiarong Li

Supersonic airflow acceleration/deceleration profile design is often incorporated as part of nozzle design and widely applied in fields such as hypersonic wind tunnels and scramjet inlet design. However, detailed research on this topic is rarely found in current literature. Profile design methods typically utilize Method of characteristics theory(MOC), which is highly sensitive to the selection of initial value lines and directly impacts the profile characteristics. Starting from the axisymmetric characteristic line theory, this paper proposes and compares three methods for obtaining initial values. Among them, the flow field calculation method exhibits the best uniformity. When combined with this method, optimizing the aspect ratio of a supersonic annular nozzle to 8.24 results in optimal flow field uniformity, with the standard deviation of the exit Mach number being less than 0.002. A variable curvature transition profile design method is proposed, achieving acceleration of airflow from Mach 2 to Mach 4 while ensuring flow field uniformity. Finally, an inverse design approach is adopted for the acceleration profile, optimizing the traditional supersonic diffuser cone section into an isentropic contraction section. At a back pressure of 90 kPa, the total pressure recovery coefficient is 2.123% higher than that of the cone section. The research results demonstrate that the methods proposed in this paper effectively address issues related to flow field uniformity and total pressure loss. Their effectiveness and versatility have been verified in acceleration profiles, annular nozzles, and diffusers, providing reliable theoretical and methodological support for the design of hypersonic engineering equipment

超声速气流加减速型线设计通常作为喷管设计的一部分，广泛应用于高超声速风洞和超燃冲压发动机进气道设计等领域。然而，在目前的文献中，对这一主题的详细研究很少。轮廓线设计方法通常采用特征理论方法（MOC），该方法对初始值线的选取高度敏感，并直接影响轮廓线的特性。从轴对称特征线理论出发，提出并比较了三种求初值的方法。其中，流场计算方法的均匀性最好。结合该方法，将超声速环形喷管展弦比优化为8.24时，流场均匀性最佳，出口马赫数标准差小于0.002。提出了一种变曲率过渡型设计方法，在保证流场均匀性的同时，实现了从2马赫到4马赫的气流加速。最后，采用逆设计方法，将传统的超声速扩压锥段优化为等熵收缩段。在背压为90 kPa时，总压恢复系数比锥段高2.123%。研究结果表明，本文提出的方法有效地解决了流场均匀性和总压损失问题。它们的有效性和通用性已经在加速剖面、环形喷管和扩散器中得到验证，为高超声速工程设备的设计提供了可靠的理论和方法支持

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引用次数: 0

Corrigendum to “Nonlinear dynamic inversion control with unknown control effectiveness and actuator dynamic [AESCTE 160 (2025), 110036]” “具有未知控制有效性和执行器动态的非线性动态反演控制[AESCTE 160(2025), 110036]”的勘误表

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2025.111606

Rui Cao , Yanbin Liu

引用次数: 0

Corrigendum to “Multi-objective Lagrangian inverse function stratified Monte Carlo method for quantifying instability risks in compressor aerodynamic systems” [Aerospace Science and Technology Volume 168, Part D (January 2026), 111065] “量化压气机气动系统不稳定风险的多目标拉格朗日逆函数分层蒙特卡罗方法”的勘误表[航空航天科学与技术卷168，D部分（2026年1月），111065]

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-01 DOI: 10.1016/j.ast.2025.111474

Yujie Zhao, Zhiping Li, Han Jiang, Lei Qi

引用次数: 0